EP2378068A2 - Damping element and method for damping blade vibrations, rotor blade and rotor - Google Patents

Damping element and method for damping blade vibrations, rotor blade and rotor Download PDF

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Publication number
EP2378068A2
EP2378068A2 EP11161054A EP11161054A EP2378068A2 EP 2378068 A2 EP2378068 A2 EP 2378068A2 EP 11161054 A EP11161054 A EP 11161054A EP 11161054 A EP11161054 A EP 11161054A EP 2378068 A2 EP2378068 A2 EP 2378068A2
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EP
European Patent Office
Prior art keywords
damping
rotor
blade
damping element
damping system
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP11161054A
Other languages
German (de)
French (fr)
Other versions
EP2378068A3 (en
EP2378068B1 (en
Inventor
Hans Peter Borufka
Andreas Hartung
Patrick Prokopczuk
Frank Stiehler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP2378068A2 publication Critical patent/EP2378068A2/en
Publication of EP2378068A3 publication Critical patent/EP2378068A3/en
Application granted granted Critical
Publication of EP2378068B1 publication Critical patent/EP2378068B1/en
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Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/42—Movement of components with two degrees of freedom
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/212—Aluminium titanate
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a damping element for damping blade vibrations of a turbomachine, a blade with such a damping system, a rotor having a plurality of such damped blades and a method for damping blade vibrations of a rotor of a turbomachine.
  • Gas turbine rotor blades such as aircraft engines are often clamped together within a blade ring via their shrouds for vibration damping.
  • shrouds as in the patent DE 40 15 206 C1
  • the applicant often shown a Z-like shape with two power transmission surfaces for mutual mechanical coupling. Although such a mechanical coupling is very effective, but the shrouds are exposed to a relatively high wear in the field of their power transmission surfaces.
  • the DE 30 08 890 discloses a rotor for a gas turbine engine having a damping weight for damping purposes, which upon rotation is forced radially outward and frictionally engages the inner surface of a platform.
  • Object of the present invention is to provide a damping system for damping blade vibrations of a turbomachine, a blade with such a damping system, a rotor having a plurality of such steamed blades.
  • An inventive damping system for damping vibrations of a blade of a rotor of a turbomachine, such as an aircraft engine has a damping element which is guided on a blade-side carrier so that it performs a radially outward movement in a rotation of the rotor centrifugally based and in contact with a lower platform portion of the blade can be brought.
  • the damping system allows damping of critical vibration modes of compressor and turbine stages with and without shroud, mounted design or integral BLISK (Bladed Disk) or BLING (Bladed Ring) construction, with or without blade cooling and with or without blade cavities.
  • the damping element is guided as a so-called riding mass (rocking damper) on the support such as a cover plate or a mini cover plate on the blade. Due to the rotation of the rotor, degrees of freedom of movement of the damping element due to a self-adjusting centrifugal force field are utilized in such a way that at one or more defined coupling contact points, at least between the blade and the independent one from the centrifugal force field tracked damping element, a contact is generated.
  • the mass of the damping element serves as an optimization parameter and for the definition of switching points between a so-called "locked and slipping" state of the damping system.
  • the damping element can also perform movements in the circumferential direction of the rotor, so that the damping element has as many degrees of freedom of movement.
  • the damping element is mounted by means of at least one connecting element on the carrier, which is guided in a radially extending longitudinal groove.
  • the longitudinal groove is preferably designed such that, when the damping element strikes the lower platform region, the connecting element is spaced from a wall section of the longitudinal groove opposite the direction of movement of the damping elements and thus relieved of load. That is, the at least one connecting element serves only as a backup, but not as a limitation of the radial movement of the damping element. The limitation is made by the lower platform area of the blade.
  • the damping element has opposite sliding surfaces for guiding along two carrier-side, radially extending guide surfaces. It is also conceivable to mount the damping element pivotably on the carrier.
  • the risk of tilting can be further reduced if the damping element is U-shaped and engages around a head portion of the carrier on both sides.
  • a peripheral contact surface formed by a survey is arranged as a stop for the damping element in the lower platform area.
  • an end-side contact surface for producing a frictional contact between the damping element and the blade can be provided. The exact position of the contact surfaces can be adjusted depending on the respective vibration shape, so that an individualized contact between the damping element and the blade takes place and vibrations can be effectively damped.
  • the abutment surfaces are arranged, for example symmetrical to the longitudinal surface of the damping element.
  • a blade according to the invention of a turbomachine for example an aircraft engine, has at least one damping system with a damping element, which is guided on a rotor-side carrier so that it performs an outward movement in the radial direction during rotation of the rotor and in abutment with a lower platform portion of the Can be brought blade.
  • the damping system can be arranged in the axial rotor direction before, behind or on both sides, ie both upstream and downstream, of the blade.
  • An inventive rotor of a turbomachine has a plurality of blades arranged in rows of blades, wherein on the blades of at least one blade row damping elements are arranged, which are guided on a rotor-side carrier that they run due to centrifugal force in the radial direction and in abutment with a lower Platform region of the blades can be brought.
  • the damping elements are preferably damped bending and torsional vibration modes. In this case, the damping effect can be optimized or increased by a geometrical adaptation of the contact geometry between the damping elements and the blades to a vibration characteristic.
  • a damping element is provided in each case in a lower platform region of the rotor blades, which is guided on a rotor-side carrier and moved against the respective lower platform region due to the centrifugal force.
  • the respective damping element rubs along an end abutment surface of the blades, so that upon rotation the damper element is not only pressed against and in frictional contact with the lower platform portion but also mechanically damped by energy dissipation as a result of dry friction between the two Damping element and the oscillating frontal contact surfaces takes place.
  • FIG. 1 shows a perspective view of a section of a blade row 2 of a rotor disk 4 in the flow direction.
  • the blade row 2 consists of a plurality of blades 6, which may be, for example, compressor or turbine blades of a stationary gas turbine or an aircraft engine. They each have an integral with the disc 4 disc web 8, an airfoil 10 and arranged between the blade web 8 and the airfoil 10 gedbeiterten body portion 12th
  • the body portion 12 has a front end face 14 oriented opposite to the flow direction, and a lower body surface 16 positioned almost at right angles thereto, which points in the direction of a rotation axis, not shown, of the rotor disk 4 and in which a circumferential groove 18 is formed.
  • the end face 14 has an annular end face 20 arranged upstream in the axial direction.
  • the end face 14 is delimited by a front platform 22, which essentially serves to reduce flow losses and in relation to a not shown rearward rear platform in the region of the body portion 12 is disposed radially outboard.
  • a damping system 26 which has a plurality of damping elements 28 which are circumferentially spaced from each other in the circumferential direction of the rotor disk 4 movably mounted on a carrier 30 in the radial direction and in the circumferential direction ,
  • the carrier 30 extends over all the blades 6 of the blade row 2 and has in the embodiment shown the shape of an annular disc 32 with a radially inner axial projection 34 which extends almost at right angles to or from this.
  • the projection 34 has in the embodiment shown a peripheral surface 36, by means of which it is in abutment with the body surface 16 of the body portion 12 and in which a circumferential groove 38 is formed to form a cavity with the circumferential groove 18 for receiving a locking ring 40.
  • the annular disc 34 is in abutment with the annular end face 20 of the body portion 12, whereby a gap 42 between the annular disc 32 and the end face 14 is formed.
  • the damping elements 28 have here, for example, each a U-shaped configuration with two identically shaped legs 44, 46, which are connected to each other via a connecting portion 48. They respectively embrace a head portion of the carrier 30 and the annular disc 32, wherein they are supported in the rest position shown with the connecting portion 48 in the radial direction on the head portion.
  • the damping elements 28 Upon rotation of the rotor disk 4, the damping elements 28 carry out a radially outward movement due to the centrifugal force, whereby they run onto a circumferential contact surface 54 of the respective front platform 22 formed by an elevation 52 with a connecting portion-side outer peripheral surface 50.
  • the abutment surface 54 is designed according to the vibration shape to be damped and positioned on the platform 22.
  • the geometry and the mass of the damping elements 28 are each adapted to the form of vibration to be damped.
  • the damping elements 28 are each about two rivet or bolt-like connecting elements 56, 58, according to FIG. 3 are inserted through in each case one damping element-side bore pair 60 and guided in carrier-side radial longitudinal grooves 64, on the carrier 30 in the radial and in the circumferential direction movable within limits.
  • the Bore pairs 60 and the longitudinal grooves 64 are formed in such a way to each other that the emergence of the damping elements 28 on the lower platforms 22, the connecting elements 56, 58 are relieved.
  • D. h. The damping elements 28 are not supported in radially disengaged position or in working position on the connecting elements 56, 58, but are spaced therefrom.
  • the damping elements 28 are based on their respective connecting portion 48 on the carrier 30, so that in the rest position, the connecting elements 56, 58 are relieved.
  • the connecting elements 56, 58 rather prevent slippage of the damping elements 28 in the circumferential direction outside the allowable limits.
  • an unnumbered survey to form an end abutment surface for the damping element 28 is formed which extends in the axial direction of the radially moving damping element 28 and designed according to the damping waveform to be damped and is positioned and with a coating may be provided for adjusting the friction behavior.
  • the front-side contact surface forms with the peripheral contact surface 54 quasi an angle profile and is arranged symmetrically to the vertical axis of the respective damping element 28 in its rest position.
  • the connecting elements 56, 58 and the longitudinal grooves 64 are arranged symmetrically to the vertical axis of the respective damping element 28 in its rest position, so that tilting or jamming of the damping elements 28 is effectively prevented in a radial movement.
  • the damping elements 28 Upon rotation of the rotor disk 4, the damping elements 28 are pressed with their outer peripheral surfaces 50 due to the centrifugal force to the outside of the peripheral contact surfaces 54. At the same time rub the damping elements 28 with the front side 14 facing legs 46 each along the end-side contact surfaces 70, so that by energy dissipation between the damper elements 28 and the oscillating contact surfaces 54, possibly also between the damper elements 28 and the carrier 30 itself, a precise mechanical Damping of the respective blade 6 and thus the entire blade row 2 takes place.
  • FIG. 4 shows a second inventive damping system 74 for damping of preferably bending and torsional vibration modes of a blade row 2.
  • the damping system 74 is based on the same principle of action as the above-described damping system 26 according to the FIGS. 1 to 3 ,
  • the main difference between the two damping systems 26, 74 is in the leadership of their damping elements 28, 78 on or on the carrier 30, 76th
  • the damping system 74 is disposed in a lower platform portion 22 and has a paddle-side support 76 on which a plurality of juxtaposed and spaced apart damping elements 78 are guided.
  • the damping elements 78 are movable at least in the radial direction and each have a symmetrical U-shaped configuration for partially encompassing a head portion of the carrier 76 with two legs 44, 46 (FIG. Fig. 6 ).
  • the guide or securing the damping elements 78 on the carrier 76 is carried out as in FIG. 5 Shown on two inside and opposite sliding surfaces 80 of their legs 44, 46 which are engaged with correspondingly formed with respect to adjacent surface portions gurge stepped and extending in the radial direction guide surfaces 84 of the carrier 76 in operative engagement.
  • the damping elements 78 are pressed by the centrifugal force against the circumferential contact surfaces 54. At the same time rub the damper elements 78 against this peripheral contact surface 54 and against the end abutment surfaces 70 of the blade 6, so that, inter alia, a mechanical damping due to the energy dissipation due to dry friction between the damping elements 78 and the oscillating contact surfaces 54, 70, optionally also between the damping elements 78 and the carrier 76 takes place.
  • a damping system for damping vibrations of a blade of a rotor of a turbomachine the damping element is guided on the blade side so that it performs a radially outward movement during rotation of the rotor and can be brought into contact with a lower platform portion of the blade, a blade With Such a damping system, a rotor having a plurality of such damping systems and a method for damping blade vibrations.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The system (26) has a damping element (28) guided on a support (30) by a connection element such that the damping element is outwardly movable during rotation of a rotor and made to contact with a lower platform area (22) of a rotor blade. A circumferential contact surface (54) is formed by an elevation (52) on the lower platform area as a limit stop for a movement of the damping element. The connection element is guided into a radially extending longitudinal groove (18) of the support. The damping element is in contact with the platform area. The connection element is released in the groove. An independent claim is also included for a rotor comprising a rotor blade with a damping system.

Description

Die Erfindung betrifft ein Dämpfungselement zur Dämpfung von Laufschaufelschwingungen einer Strömungsmaschine, eine Laufschaufel mit einem derartigen Dämpfungssystem, einen Rotor mit einer Vielzahl derartig gedämpfter Laufschaufeln und ein Verfahren zur Dämpfung von Laufschaufelschwingungen eines Rotors einer Strömungsmaschine.The invention relates to a damping element for damping blade vibrations of a turbomachine, a blade with such a damping system, a rotor having a plurality of such damped blades and a method for damping blade vibrations of a rotor of a turbomachine.

Laufschaufeln von Gasturbinen wie Flugzeugtriebwerke sind zur Schwingungsdämpfung häufig innerhalb eines Schaufelkranzes über ihre Deckbänder miteinander verspannt. Hierzu haben die Deckbänder wie in dem Patent DE 40 15 206 C1 der Anmelderin gezeigt häufig eine Z-artige Gestalt mit jeweils zwei Kraftübertragungsflächen zur gegenseitigen mechanischen Kopplung. Eine derartige mechanische Kopplung ist zwar sehr effektiv, jedoch sind die Deckbänder im Bereich ihrer Kraftübertragungsflächen einem relativ hohen Verschleiß ausgesetzt.Gas turbine rotor blades, such as aircraft engines, are often clamped together within a blade ring via their shrouds for vibration damping. For this purpose, have the shrouds as in the patent DE 40 15 206 C1 The applicant often shown a Z-like shape with two power transmission surfaces for mutual mechanical coupling. Although such a mechanical coupling is very effective, but the shrouds are exposed to a relatively high wear in the field of their power transmission surfaces.

Darüber hinaus ist es aus der EP 0 511 022 B1 bekannt, Laufschaufel über ein drahtartiges Dämpfungselement miteinander zu verspannen, das durch die Schaufelblätter geführt ist. Diese Lösung hat jedoch insbesondere den Nachteil, dass sich das drahtartige Dämpfungselement im Strömungspfad bzw. Ringraumkanal befindet. Insbesondere ist diese Lösung nicht bzw. nur bedingt bei innen gekühlten Schaufeln anwendbar.In addition, it is from the EP 0 511 022 B1 known to brace blade via a wire-like damping element, which is guided by the blades. However, this solution has the particular disadvantage that the wire-like damping element is located in the flow path or annulus channel. In particular, this solution is not or only partially applicable to internally cooled blades.

Darüber hinaus ist es aus der europäischen Patentanmeldung EP 1 944 466 A1 bekannt, Dämpfungselemente in Taschen von benachbarten Deckbändern anzuordnen. Bei einer Rotation des Rotors werden die Dämpfungselemente aufgrund der Fliehkraft radial nach außen bewegt und bewirken somit eine mechanische Kopplung der Deckbänder. Eine optimale Einstellung der Schwingungsdämpfung ist jedoch mit diesem System nicht möglich.In addition, it is from the European patent application EP 1 944 466 A1 known to arrange damping elements in pockets of adjacent shrouds. During a rotation of the rotor, the damping elements are moved radially outwardly due to the centrifugal force and thus cause a mechanical coupling of the shrouds. An optimal adjustment of the vibration damping is not possible with this system.

Ferner ist es aus der US 3,307,741 bekannt, ein auf Fliehkraft basierendes Dämpfungssystem zu verwenden, dessen Dämpfungselemente in einem Zwischenraum zwischen zwei benachbarten Laufschaufeln angeordnet sind, der in radialer Richtung von deren Plattformen begrenzt ist. Die Dämpfungselemente sind jeweils über einen Stift in einer Rotorbohrung in radialer Richtung verschiebbar geführt sind und können somit bei einer Rotation gegen untere Bereiche der Plattformen auflaufen. Derartige Dämpfungselemente bieten jedoch aufgrund ihrer Topologie keine ausreichende Dämpfung insbesondere von Torsionsschwingungsformen. Außerdem ist der zur Verfügung stehende konstruktive Gestaltungsraum sehr begrenzt, so dass die Gestaltung und Größe dieser Dämpfungselemente ihre Auslegungs- und Umsetzungsanforderungen nur bedingt respektive nicht erfüllen.Furthermore, it is from the US 3,307,741 It is known to use a centrifugal damping system, the damping elements of which are arranged in a space between two adjacent blades, which is bounded in the radial direction of their platforms. The damping elements are each via a pin in a rotor bore in the radial direction slidably guided and can thus accumulate in a rotation against lower areas of the platforms. However, due to their topology, such damping elements do not provide sufficient damping, in particular of torsional vibration modes. In addition, the available design space is very limited, so that the design and size of these damping elements their interpretation and implementation requirements only conditionally respectively do not meet.

Die DE 30 08 890 offenbart einen Rotor für ein Gasturbinentriebwerk, das zu Dämpfungszwecken ein Dämpfungsgewicht aufweist, das bei Rotation radial nach außen gedrückt wird und reibschlüssig an der inneren Oberfläche einer Plattform angreift.The DE 30 08 890 discloses a rotor for a gas turbine engine having a damping weight for damping purposes, which upon rotation is forced radially outward and frictionally engages the inner surface of a platform.

Aufgabe der vorliegenden Erfindung ist es, ein Dämpfungssystem zur Dämpfung von Laufschaufelschwingungen einer Strömungsmaschine, eine Laufschaufel mit einem derartigen Dämpfungssystem, einen Rotor mit einer Vielzahl von derartig gedämpften Laufschaufeln zu schaffen.Object of the present invention is to provide a damping system for damping blade vibrations of a turbomachine, a blade with such a damping system, a rotor having a plurality of such steamed blades.

Diese Aufgabe wird gelöst durch ein Dämpfungssystem mit den Merkmalen des Patentanspruchs 1, durch eine Laufschaufel mit den Merkmalen des Patentanspruchs 11 und durch einen Rotor mit den Merkmalen des Patentanspruchs 12.This object is achieved by a damping system having the features of patent claim 1, by a rotor blade having the features of patent claim 11 and by a rotor having the features of patent claim 12.

Ein erfindungsgemäßes Dämpfungssystem zur Dämpfung von Schwingungen einer Laufschaufel eines Rotors einer Strömungsmaschine, beispielsweise eines Flugzeugtriebwerks, hat ein Dämpfungselement, das an einem schaufelseitigen Träger so geführt ist, dass es bei einer Rotation des Rotors fliehkraftbasierend eine radial nach außen gerichtete Bewegung ausführt und in Anlage mit einem unteren Plattformbereich der Laufschaufel bringbar ist.An inventive damping system for damping vibrations of a blade of a rotor of a turbomachine, such as an aircraft engine, has a damping element which is guided on a blade-side carrier so that it performs a radially outward movement in a rotation of the rotor centrifugally based and in contact with a lower platform portion of the blade can be brought.

Das erfindungsgemäße Dämpfungssystem erlaubt eine Dämpfung von kritischen Schwingungsformen von Verdichter- und Turbinenlaufstufen mit und ohne Deckband, in montierter Bauweise oder integraler BLISK- (Bladed Disk) bzw. BLING- (Bladed Ring) Bauweise, mit oder ohne Schaufelkühlung sowie mit oder ohne Schaufelhohlräumen. Das Dämpfungselement ist als sogenannte reitende Masse (Rocking Damper) auf den Träger wie beispielsweise einem Coverplate oder einem Mini-Coverplate an der Laufschaufel geführt. Durch die Rotation des Rotors werden Bewegungsfreiheitsgrade des Dämpfungselementes aufgrund eines sich einstellenden Fliehkraftfeldes so ausgenutzt, dass an einer oder mehreren definierten Koppel-Kontakt-Stellen zumindest zwischen der Laufschaufel und dem selbstständig vom Fliehkraftfeld nachgeführten Dämpfungselement ein Kontakt erzeugt wird. Dabei dient die Masse des Dämpfungselementes als Optimierungsparameter und zur Definition von Schaltpunkten zwischen einem sogenannten "locked und slipping" Zustand des Dämpfungssystems.The damping system according to the invention allows damping of critical vibration modes of compressor and turbine stages with and without shroud, mounted design or integral BLISK (Bladed Disk) or BLING (Bladed Ring) construction, with or without blade cooling and with or without blade cavities. The damping element is guided as a so-called riding mass (rocking damper) on the support such as a cover plate or a mini cover plate on the blade. Due to the rotation of the rotor, degrees of freedom of movement of the damping element due to a self-adjusting centrifugal force field are utilized in such a way that at one or more defined coupling contact points, at least between the blade and the independent one from the centrifugal force field tracked damping element, a contact is generated. The mass of the damping element serves as an optimization parameter and for the definition of switching points between a so-called "locked and slipping" state of the damping system.

Vorzugsweise kann das Dämpfungselement ebenfalls Bewegungen in Umfangsrichtung des Rotors ausführen, so dass das Dämpfungselement möglichst viele Bewegungsfreiheitsgrade aufweist.Preferably, the damping element can also perform movements in the circumferential direction of the rotor, so that the damping element has as many degrees of freedom of movement.

Bei einem Ausführungsbeispiel ist das Dämpfungselement mittels zumindest eines Verbindungselementes an dem Träger gelagert, das in einer sich radial erstreckenden Längsnut geführt ist. Dabei ist die Längsnut vorzugsweise derart ausgeführt, dass beim Auflaufen des Dämpfungselementes auf den unteren Plattformbereich das Verbindungselement von einem in Bewegungsrichtung des Dämpfungselemente betrachtet gegenüberliegenden Wandungsabschnitt der Längsnut beabstandet und somit entlastet ist. Das heißt, das zumindest eine Verbindungselement dient lediglich als Sicherung, nicht jedoch als Begrenzung der radialen Bewegung des Dämpfungselementes. Die Begrenzung erfolgt durch den unteren Plattformbereich der Schaufel.In one embodiment, the damping element is mounted by means of at least one connecting element on the carrier, which is guided in a radially extending longitudinal groove. In this case, the longitudinal groove is preferably designed such that, when the damping element strikes the lower platform region, the connecting element is spaced from a wall section of the longitudinal groove opposite the direction of movement of the damping elements and thus relieved of load. That is, the at least one connecting element serves only as a backup, but not as a limitation of the radial movement of the damping element. The limitation is made by the lower platform area of the blade.

Bei einem anderen Ausführungsbeispiel weist das Dämpfungselement gegenüberliegende Gleitflächen zur Führung entlang zwei trägerseitiger, radial verlaufender Führungsflächen auf. Ebenso ist es vorstellbar, das Dämpfungselement verschwenkbar an dem Träger zu lagern.In another embodiment, the damping element has opposite sliding surfaces for guiding along two carrier-side, radially extending guide surfaces. It is also conceivable to mount the damping element pivotably on the carrier.

Die Gefahr des Verkantens lässt sich weiter reduzieren, wenn das Dämpfungselement U-förmig ausgebildet ist und einen Kopfabschnitt des Trägers beidseitig umgreift.The risk of tilting can be further reduced if the damping element is U-shaped and engages around a head portion of the carrier on both sides.

Vorzugsweise ist im unteren Plattformbereich eine von einer Erhebung gebildete umfangsseitige Anlagefläche als Anschlag für das Dämpfungselement angeordnet. Zusätzlich kann eine stirnseitige Anlagefläche zur Herstellung eines Reibkontaktes zwischen dem Dämpfungselement und der Laufschaufel vorgesehen sein. Die genaue Lage der Anlageflächen kann in Abhängigkeit der jeweiligen Schwingform eingestellt werden, so dass eine individualisierte Kontaktaufnahme zwischen dem Dämpfungselement und der Laufschaufel erfolgt und Schwingungen wirkungsvoll gedämpft werden können. Bei einem Ausführungsbeispiel sind die Anlageflächen zum Beispiel symmetrisch zur Längsfläche des Dämpfungselementes angeordnet.Preferably, a peripheral contact surface formed by a survey is arranged as a stop for the damping element in the lower platform area. In addition, an end-side contact surface for producing a frictional contact between the damping element and the blade can be provided. The exact position of the contact surfaces can be adjusted depending on the respective vibration shape, so that an individualized contact between the damping element and the blade takes place and vibrations can be effectively damped. In one embodiment, the abutment surfaces are arranged, for example symmetrical to the longitudinal surface of the damping element.

Eine erfindungsgemäße Laufschaufel einer Strömungsmaschine, beispielsweise eines Flugzeugtriebwerks, hat zumindest ein Dämpfungssystem mit einem Dämpfungselement, das an einem rotorseitigen Träger so geführt ist, dass es bei einer Rotation des Rotors eine nach außen gerichtete Bewegung in Radialrichtung ausführt und in Anlage mit einem unteren Plattformbereich der Laufschaufel bringbar ist. Das Dämpfungssystem kann in axialer Rotorrichtung vor, hinter oder beidseits, also sowohl stromaufwärts als auch stromabwärts, der Laufschaufel angeordnet sein.A blade according to the invention of a turbomachine, for example an aircraft engine, has at least one damping system with a damping element, which is guided on a rotor-side carrier so that it performs an outward movement in the radial direction during rotation of the rotor and in abutment with a lower platform portion of the Can be brought blade. The damping system can be arranged in the axial rotor direction before, behind or on both sides, ie both upstream and downstream, of the blade.

Ein erfindungsgemäßer Rotor einer Strömungsmaschine hat eine Vielzahl von in Schaufelreihen angeordneten Laufschaufeln, wobei an den Laufschaufeln zumindest einer Schaufelreihe Dämpfungselemente angeordnet sind, die so an einem rotorseitigen Träger geführt sind, dass sie aufgrund der Fliehkraft eine Bewegung in Radialrichtung ausführen und in Anlage mit einem unteren Plattformbereich der Laufschaufeln bringbar sind. Durch die Dämpfungselemente werden vorzugsweise Biege- und Torsionsschwingungsformen gedämpft. Dabei kann durch eine geometrische Anpassung der Kontaktgeometrie zwischen den Dämpfungselementen und den Laufschaufeln an eine Schwingungsformcharakteristik die Dämpfungswirkung optimiert respektive gesteigert werden.An inventive rotor of a turbomachine has a plurality of blades arranged in rows of blades, wherein on the blades of at least one blade row damping elements are arranged, which are guided on a rotor-side carrier that they run due to centrifugal force in the radial direction and in abutment with a lower Platform region of the blades can be brought. By the damping elements are preferably damped bending and torsional vibration modes. In this case, the damping effect can be optimized or increased by a geometrical adaptation of the contact geometry between the damping elements and the blades to a vibration characteristic.

Bei einem erfindungsgemäßen Verfahren zum Dämpfen von Schwingungen von Laufschaufeln einer Strömungsmaschine, beispielsweise eines Flugzeugtriebwerks, wird jeweils in einem unteren Plattformbereich der Laufschaufeln ein Dämpfungselement vorgesehen, das an einem rotorseitigen Träger geführt und aufgrund der Fliehkraft gegen den jeweiligen unteren Plattformbereich bewegt wird.In a method according to the invention for damping vibrations of moving blades of a turbomachine, for example an aircraft engine, a damping element is provided in each case in a lower platform region of the rotor blades, which is guided on a rotor-side carrier and moved against the respective lower platform region due to the centrifugal force.

Bei einem bevorzugten Ausführungsbeispiel reibt das jeweilige Dämpfungselement entlang einer stirnseitigen Anlagefläche der Laufschaufeln, so dass bei einer Rotation das Dämpferelement nicht nur an den unteren Plattformbereich gedrückt wird und mit diesem in Reibkontakt steht, sondern ebenfalls eine mechanische Dämpfung durch Energiedissipation in Folge trockener Reibung zwischen dem Dämpfungselement und der schwingenden stirnseitigen Anlageflächen erfolgt. Gegebenenfalls erfolgt ebenfalls eine mechanische Dämpfung zwischen dem Dämpferelement und dem Träger.In a preferred embodiment, the respective damping element rubs along an end abutment surface of the blades, so that upon rotation the damper element is not only pressed against and in frictional contact with the lower platform portion but also mechanically damped by energy dissipation as a result of dry friction between the two Damping element and the oscillating frontal contact surfaces takes place. Optionally, there is also a mechanical damping between the damper element and the carrier.

Sonstige vorteilhafte Ausführungsbeispiele der vorliegenden Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the present invention are the subject of further subclaims.

Im Folgenden werden bevorzugte Ausführungsbeispiele der vorliegenden Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigen:

  • Figur 1 eine perspektivische Darstellung eines ersten erfindungsgemäßen Dämpfungssystems,
  • Figur 2 eine Detaildarstellung des ersten Dämpfungssystems,
  • Figur 3 einen Querschnitt durch das erste Dämpfungssystems,
  • Figur 4 eine perspektivische Darstellung eines zweiten erfindungsgemäßen Dämpfungssystems, und
  • Figur 5 eine Detaildarstellung des zweiten Dämpfungselements, und
  • Figur 6 einen Querschnitt durch das zweite Dämpfungssystems,
In the following, preferred embodiments of the present invention are explained in more detail with reference to schematic representations. Show it:
  • FIG. 1 a perspective view of a first damping system according to the invention,
  • FIG. 2 a detailed representation of the first damping system,
  • FIG. 3 a cross section through the first damping system,
  • FIG. 4 a perspective view of a second damping system according to the invention, and
  • FIG. 5 a detailed representation of the second damping element, and
  • FIG. 6 a cross section through the second damping system,

In den Figuren tragen gleiche konstruktive Elemente die gleichen Bezugsziffern, wobei bei mehreren gleichen konstruktiven Elementen in einer Figur aus Gründen der Übersichtlichkeit lediglich ein Element mit der jeweiligen Bezugsziffer versehen ist.In the figures, the same structural elements bear the same reference numerals, with several identical structural elements in a figure for reasons of clarity, only one element is provided with the respective reference numeral.

Figur 1 zeigt einen perspektiven Blick auf einen Ausschnitt einer Schaufelreihe 2 einer Rotorscheibe 4 in Strömungsrichtung. Die Schaufelreihe 2 besteht aus einer Vielzahl von Laufschaufeln 6, die beispielsweise Verdichter- oder Turbinenschaufeln einer stationären Gasturbine oder eines Flugzeugtriebwerks sein können. Sie haben jeweils einen integral mit der Scheibe 4 gefügten Scheibensteg 8, ein Schaufelblatt 10 sowie einen zwischen dem Schaufelsteg 8 und dem Schaufelblatt 10 angeordneten verbeiterten Körperabschnitt 12. FIG. 1 shows a perspective view of a section of a blade row 2 of a rotor disk 4 in the flow direction. The blade row 2 consists of a plurality of blades 6, which may be, for example, compressor or turbine blades of a stationary gas turbine or an aircraft engine. They each have an integral with the disc 4 disc web 8, an airfoil 10 and arranged between the blade web 8 and the airfoil 10 gedbeiterten body portion 12th

Wie in Figur 2 gezeigt hat der Körperabschnitt 12 eine entgegengesetzt zur Strömungsrichtung orientierte vordere Stirnfläche 14, und eine nahezu rechtwinklig zu dieser angestellte untere Körperfläche 16, die in Richtung einer nicht gezeigten Rotationsachse der Rotorscheibe 4 zeigt und in der eine Umfangsnut 18 ausgebildet ist. Im Kantenbereich mit der Körperfläche 16 weist die Stirnfläche 14 eine in axialer Richtung vorgelagerte Ringstirnfläche 20 auf. In radialer Richtung wird die Stirnfläche 14 von einer vorderen Plattform 22 begrenzt, die im Wesentlichen zur Reduzierung von Strömungsverlusten dient und gegenüber einer nicht gezeigten rückwärtigen hinteren Plattform im Bereich des Körperabschnitts 12 radial außenliegend angeordnet ist.As in FIG. 2 1, the body portion 12 has a front end face 14 oriented opposite to the flow direction, and a lower body surface 16 positioned almost at right angles thereto, which points in the direction of a rotation axis, not shown, of the rotor disk 4 and in which a circumferential groove 18 is formed. In the edge region with the body surface 16, the end face 14 has an annular end face 20 arranged upstream in the axial direction. In the radial direction, the end face 14 is delimited by a front platform 22, which essentially serves to reduce flow losses and in relation to a not shown rearward rear platform in the region of the body portion 12 is disposed radially outboard.

Unterhalb der vorderen Plattform 22, d. h. zwischen der vorderen Plattform 22 und einem nicht gezeigten Außenumfangsabschnitt der Rotorscheibe 4, ist ein erfindungsgemäßes Dämpfungssystem 26 angeordnet, das eine Vielzahl von Dämpfungselementen 28 aufweist, die in Umfangsrichtung der Rotorscheibe 4 nebeneinanderliegend voneinander beabstandet auf einem Träger 30 in Radialrichtung und in Umfangsrichtung bewegbar gelagert sind.Below the front platform 22, d. H. between the front platform 22 and an outer peripheral portion of the rotor disk 4, not shown, a damping system 26 according to the invention is arranged, which has a plurality of damping elements 28 which are circumferentially spaced from each other in the circumferential direction of the rotor disk 4 movably mounted on a carrier 30 in the radial direction and in the circumferential direction ,

Der Träger 30 erstreckt sich über sämtliche Laufschaufeln 6 der Schaufelreihe 2 und hat in dem gezeigten Ausführungsbeispiel die Gestalt einer Ringscheibe 32 mit einem radial innenliegenden axialen Vorsprung 34, der sich nahezu rechtwinklig zur bzw. von dieser erstreckt. Der Vorsprung 34 hat in dem gezeigten Ausführungsbeispiel eine Umfangsfläche 36, mittels der er sich in Anlage mit der Körperfläche 16 des Körperabschnitts 12 befindet und in der eine Umfangsnut 38 zur Bildung eines Hohlraums mit der Umfangsnut 18 zur Aufnahme eines Sicherungsrings 40 ausgebildet ist. Die Ringscheibe 34 befindet sich in Anlage mit der Ringstirnfläche 20 des Körperabschnitts 12, wodurch ein Spalt 42 zwischen der Ringscheibe 32 und der Stirnfläche 14 gebildet ist.The carrier 30 extends over all the blades 6 of the blade row 2 and has in the embodiment shown the shape of an annular disc 32 with a radially inner axial projection 34 which extends almost at right angles to or from this. The projection 34 has in the embodiment shown a peripheral surface 36, by means of which it is in abutment with the body surface 16 of the body portion 12 and in which a circumferential groove 38 is formed to form a cavity with the circumferential groove 18 for receiving a locking ring 40. The annular disc 34 is in abutment with the annular end face 20 of the body portion 12, whereby a gap 42 between the annular disc 32 and the end face 14 is formed.

Die Dämpfungselemente 28 haben hier beispielsweise jeweils eine U-förmige Gestalt mit zwei gleich ausgebildeten Schenkeln 44, 46, die über einen Verbindungsabschnitt 48 miteinander verbunden sind. Sie umgreifen jeweils einen Kopfabschnitt des Trägers 30 bzw. der Ringscheibe 32, wobei sie sich in der gezeigten Ruheposition mit dem Verbindungsabschnitt 48 in radialer Richtung auf dem Kopfabschnitt abstützen. Bei einer Rotation der Rotorscheibe 4 führen die Dämpfungselemente 28 aufgrund der Fliehkraft eine radial nach außen gerichtete Bewegung aus, wobei sie mit einer verbindungsabschnittsseitigen Außenumfangsfläche 50 auf eine von einer Erhebung 52 gebildeten umfangsseitigen Anlagefläche 54 der jeweiligen vorderen Plattform 22 auflaufen. Die Anlagefläche 54 ist entsprechend der zu dämpfenden Schwingungsform gestaltet und an der Plattform 22 positioniert. Ebenso sind die Geometrie und die Masse der Dämpfungselemente 28 jeweils an die zu dämpfende Schwingungsform angepasst.The damping elements 28 have here, for example, each a U-shaped configuration with two identically shaped legs 44, 46, which are connected to each other via a connecting portion 48. They respectively embrace a head portion of the carrier 30 and the annular disc 32, wherein they are supported in the rest position shown with the connecting portion 48 in the radial direction on the head portion. Upon rotation of the rotor disk 4, the damping elements 28 carry out a radially outward movement due to the centrifugal force, whereby they run onto a circumferential contact surface 54 of the respective front platform 22 formed by an elevation 52 with a connecting portion-side outer peripheral surface 50. The abutment surface 54 is designed according to the vibration shape to be damped and positioned on the platform 22. Likewise, the geometry and the mass of the damping elements 28 are each adapted to the form of vibration to be damped.

Die Dämpfungselemente 28 sind über jeweils zwei nieten- bzw. bolzenartige Verbindungselemente 56, 58, die gemäß Figur 3 durch jeweils ein dämpfungselementenseitiges Bohrungspaar 60 gesteckt und in trägerseitigen radialen Längsnuten 64 geführt sind, an dem Träger 30 in radialer sowie in umfangsseitiger Richtung in Grenzen beweglich gesichert. Die Bohrungspaare 60 und die Längsnuten 64 sind dabei derart zueinander ausgebildet, dass beim Auflaufen der Dämpfungselemente 28 auf die untere Plattformen 22 die Verbindungselemente 56, 58 entlastet sind. D. h., die Dämpfungselemente 28 stützen sich in radial ausgerückter Position bzw. in Arbeitsposition nicht an den Verbindungselementen 56, 58 ab, sondern sind von diesen beabstandet. In der Ruheposition stützen sich die Dämpfungselemente 28 hingegen über ihren jeweiligen Verbindungsabschnitt 48 auf dem Träger 30 auf, so dass auch in der Ruheposition die Verbindungselemente 56, 58 entlastet sind. Somit verhindern die Verbindungselemente 56, 58 vielmehr ein Verrutschen der Dämpfungselemente 28 in Umfangrichtung außerhalb der zulässigen Grenzen.The damping elements 28 are each about two rivet or bolt-like connecting elements 56, 58, according to FIG. 3 are inserted through in each case one damping element-side bore pair 60 and guided in carrier-side radial longitudinal grooves 64, on the carrier 30 in the radial and in the circumferential direction movable within limits. The Bore pairs 60 and the longitudinal grooves 64 are formed in such a way to each other that the emergence of the damping elements 28 on the lower platforms 22, the connecting elements 56, 58 are relieved. D. h., The damping elements 28 are not supported in radially disengaged position or in working position on the connecting elements 56, 58, but are spaced therefrom. In the rest position, however, the damping elements 28 are based on their respective connecting portion 48 on the carrier 30, so that in the rest position, the connecting elements 56, 58 are relieved. Thus, the connecting elements 56, 58 rather prevent slippage of the damping elements 28 in the circumferential direction outside the allowable limits.

Unterhalb der vorderen Plattformen 22 im Bereich der Stirnfläche 14 ist eine nicht bezifferte Erhebung zur Bildung einer stirnseitigen Anlagefläche für das Dämpfungselements 28 gebildet, die sich in axialer Richtung des sich radial bewegenden Dämpfungselements 28 erstreckt und entsprechend der zu dämpfenden Schwingungsform gestaltet sowie positioniert ist und mit einer Beschichtung zur Einstellung des Reibverhaltens versehen sein kann. Die stirnseitige Anlagefläche bildet mit der umfangsseitigen Anlagefläche 54 quasi ein Winkelprofil und ist symmetrisch zur Hochachse des jeweiligen Dämpfungselements 28 in seiner Ruheposition angeordnet. Ebenso sind die Verbindungselemente 56, 58 bzw. die Längsnuten 64 symmetrisch zur Hochachse des jeweiligen Dämpfungselements 28 in seiner Ruheposition angeordnet, so dass ein Verkanten oder Klemmen der Dämpfungselemente 28 bei einer radialen Bewegung wirkungsvoll verhindert wird.Below the front platforms 22 in the region of the end face 14 is an unnumbered survey to form an end abutment surface for the damping element 28 is formed which extends in the axial direction of the radially moving damping element 28 and designed according to the damping waveform to be damped and is positioned and with a coating may be provided for adjusting the friction behavior. The front-side contact surface forms with the peripheral contact surface 54 quasi an angle profile and is arranged symmetrically to the vertical axis of the respective damping element 28 in its rest position. Likewise, the connecting elements 56, 58 and the longitudinal grooves 64 are arranged symmetrically to the vertical axis of the respective damping element 28 in its rest position, so that tilting or jamming of the damping elements 28 is effectively prevented in a radial movement.

Bei einer Rotation der Rotorscheibe 4 werden die Dämpfungselemente 28 mit ihren Außenumfangsflächen 50 aufgrund der Fliehkraft nach außen an die umfangsseitigen Anlageflächen 54 gedrückt. Gleichzeitig reiben die Dämpfungselemente 28 mit dem der Stirnseite 14 zugewandten Schenkel 46 jeweils entlang der stirnseitigen Anlageflächen 70, so dass durch Energiedissipation zwischen den Dämpferelementen 28 und den schwingenden Anlageflächen 54, gegebenenfalls auch zwischen den Dämpferelementen 28 und dem Träger 30 an sich, eine präzise mechanische Dämpfung der jeweiligen Laufschaufel 6 und somit der gesamten Schaufelreihe 2 erfolgt.Upon rotation of the rotor disk 4, the damping elements 28 are pressed with their outer peripheral surfaces 50 due to the centrifugal force to the outside of the peripheral contact surfaces 54. At the same time rub the damping elements 28 with the front side 14 facing legs 46 each along the end-side contact surfaces 70, so that by energy dissipation between the damper elements 28 and the oscillating contact surfaces 54, possibly also between the damper elements 28 and the carrier 30 itself, a precise mechanical Damping of the respective blade 6 and thus the entire blade row 2 takes place.

Figur 4 zeigt ein zweites erfindungsgemäßes Dämpfungssystem 74 zur Dämpfung von vorzugsweise Biege- und Torsionsschwingungsformen einer Laufschaufelreihe 2. Das Dämpfungssystem 74 basiert auf dem gleichen Wirkprinzip wie das vorbeschriebene Dämpfungssystem 26 nach den Figuren 1 bis 3. Der Wesentliche Unterschied zwischen den beiden Dämpfungssystemen 26, 74 besteht in der Führung ihrer Dämpfungselemente 28, 78 auf bzw. an dem Träger 30, 76. FIG. 4 shows a second inventive damping system 74 for damping of preferably bending and torsional vibration modes of a blade row 2. The damping system 74 is based on the same principle of action as the above-described damping system 26 according to the FIGS. 1 to 3 , The main difference between the two damping systems 26, 74 is in the leadership of their damping elements 28, 78 on or on the carrier 30, 76th

Das Dämpfungssystem 74 ist in einem unteren Plattformbereich 22 angeordnet und hat einen schaufelseitigen Träger 76, auf dem eine Vielzahl von nebeneinander angeordneten und voneinander beabstandeten Dämpfungselementen 78 geführt sind. Die Dämpfungselemente 78 sind zumindest in radialer Richtung bewegbar und haben jeweils eine symmetrische U-förmige Gestalt zum abschnittsweisen Umgreifen eines Kopfabschnitts des Trägers 76 mit zwei Schenkeln 44, 46 (Fig. 6).The damping system 74 is disposed in a lower platform portion 22 and has a paddle-side support 76 on which a plurality of juxtaposed and spaced apart damping elements 78 are guided. The damping elements 78 are movable at least in the radial direction and each have a symmetrical U-shaped configuration for partially encompassing a head portion of the carrier 76 with two legs 44, 46 (FIG. Fig. 6 ).

Die Führung bzw. Sicherung der Dämpfungselemente 78 an dem Träger 76 erfolgt wie in Figur 5 gezeigt über zwei innenseitig angeordnete und gegenüberliegende Gleitflächen 80 ihrer Schenkel 44, 46, die mit entsprechend ausgebildeten gegenüber benachbarten Flächenabschnitten zurückgestuften und sich in radialer Richtung erstreckenden Führungsflächen 84 des Trägers 76 im Wirkeingriff befinden.The guide or securing the damping elements 78 on the carrier 76 is carried out as in FIG. 5 Shown on two inside and opposite sliding surfaces 80 of their legs 44, 46 which are engaged with correspondingly formed with respect to adjacent surface portions rückge stepped and extending in the radial direction guide surfaces 84 of the carrier 76 in operative engagement.

Zur Optimierung der Dämpfungseigenschaften ist wie bei dem vorbeschriebenen ersten Dämpfungssystem 26 nach den Figuren 1 bis 3 im Bereich unterhalb der vorderen Plattformen 22 jeweils eine umfangsseitige Anlagefläche 54 und eine stirnseitige Anlagefläche 70 (s. Fig. 6) vorgesehen, die ein Winkelprofil bilden und symmetrisch zur Führung bzw. zur Hochachse des Dämpfungselemente 78 in Ruheposition angeordnet sind.To optimize the damping properties is as in the above-described first damping system 26 after the FIGS. 1 to 3 in the area below the front platforms 22 each have a peripheral contact surface 54 and an end-face contact surface 70 (s. Fig. 6 ), which form an angle profile and are arranged symmetrically to the guide or to the vertical axis of the damping elements 78 in the rest position.

Bei einer Rotation der Rotorscheibe 4 werden die Dämpfungselemente 78 durch die Fliehkraft an die umfangsseitigen Anlageflächen 54 gedrückt. Gleichzeitig reiben die Dämpferelemente 78 gegen diese umfangsseitigen Anlagefläche 54 sowie gegen die stirnseitigen Anlageflächen 70 der Laufschaufel 6, so dass unter anderem eine mechanische Dämpfung durch die Energiedissipation infolge trockener Reibung zwischen den Dämpfungselementen 78 und den schwingenden Anlageflächen 54, 70, gegebenenfalls auch zwischen den Dämpfungselementen 78 und dem Träger 76 erfolgt.During a rotation of the rotor disk 4, the damping elements 78 are pressed by the centrifugal force against the circumferential contact surfaces 54. At the same time rub the damper elements 78 against this peripheral contact surface 54 and against the end abutment surfaces 70 of the blade 6, so that, inter alia, a mechanical damping due to the energy dissipation due to dry friction between the damping elements 78 and the oscillating contact surfaces 54, 70, optionally also between the damping elements 78 and the carrier 76 takes place.

Offenbart ist ein Dämpfungssystem zur Dämpfung von Schwingungen einer Laufschaufel eines Rotors einer Strömungsmaschine, dessen Dämpfungselement schaufelseitig derart geführt ist, dass es bei einer Rotation des Rotors eine radial nach außen gerichtete Bewegung ausführt und in Anlage mit einem unteren Plattformbereich der Laufschaufel bringbar ist, eine Laufschaufel mit einem derartigen Dämpfungssystem, ein Rotor mit einer Vielzahl derartiger Dämpfungssysteme sowie ein Verfahren zum Dämpfen von Laufschaufelschwingungen.Disclosed is a damping system for damping vibrations of a blade of a rotor of a turbomachine, the damping element is guided on the blade side so that it performs a radially outward movement during rotation of the rotor and can be brought into contact with a lower platform portion of the blade, a blade With Such a damping system, a rotor having a plurality of such damping systems and a method for damping blade vibrations.

Claims (11)

Dämpfungssystem (26; 74) zur Dämpfung von Schwingungen einer Laufschaufel (6) eines Rotors einer Strömungsmaschine, beispielsweise eines Flugzeugtriebwerks, mit einem Dämpfungselement (28; 78), das an einem rotorseitigen Träger (30; 76) so geführt ist, dass es bei einer Rotation des Rotors eine radial nach außen gerichtete Bewegung ausführt und in Anlage mit einem unteren Plattformbereich (22) der Laufschaufel (6) bringbar ist, dadurch gekennzeichnet, dass im unteren Plattformbereich (22) eine von einer Erhebung (52) gebildete umfangsseitige Anlagefläche (54) als Anschlag für das Dämpfungselement (28; 78) angeordnet ist.A damping system (26; 74) for damping vibrations of a rotor blade (6) of a turbomachine, for example an aircraft engine, comprising a damping element (28; 78) guided on a rotor-side support (30; a rotation of the rotor carries out a radially outward movement and in abutment with a lower platform portion (22) of the blade (6) can be brought, characterized in that in the lower platform region (22) formed by a survey (52) circumferential contact surface ( 54) is arranged as a stop for the damping element (28, 78). Dämpfungssystem nach Anspruch 1, wobei das Dämpfungselement (28; 78) Bewegungen in Umfangsrichtung ausführt.A damping system according to claim 1, wherein the damping element (28; 78) performs movements in the circumferential direction. Dämpfungssystem nach Anspruch 1 oder 2, wobei das Dämpfungselement (28) mittels zumindest eines Verbindungselements (56, 58) an dem Träger (30) gelagert ist, das in einer sich radial erstreckenden Längsnut (64) geführt ist.Damping system according to claim 1 or 2, wherein the damping element (28) by means of at least one connecting element (56, 58) is mounted on the carrier (30) which is guided in a radially extending longitudinal groove (64). Dämpfungssystem nach Anspruch 3, wobei beim Auflaufen des Dämpfungselements (28) auf den unteren Plattformbereich (22) das Verbindungselement (56, 58) entlastet ist.Damping system according to claim 3, wherein during the emergence of the damping element (28) on the lower platform portion (22), the connecting element (56, 58) is relieved. Dämpfungssystem nach Anspruch 3, wobei das Dämpfungselement (78) gegenüberliegende Gleitflächen (80) zur Führung entlang zwei trägerseitiger Führungsflächen (84) hat.Damping system according to claim 3, wherein the damping element (78) has opposite sliding surfaces (80) for guiding along two carrier-side guide surfaces (84). Dämpfungssystem nach einem der vorhergehenden Ansprüche, wobei das Dämpfungselement (28; 78) U-förmig ausgebildet ist und den Träger (30; 76) abschnittsweise umgreift.Damping system according to one of the preceding claims, wherein the damping element (28; 78) is U-shaped and surrounds the carrier (30; 76) in sections. Dämpfungssystem nach einem der vorhergehenden Ansprüche, wobei eine stirnseitige Anlagefläche (70) zur Herstellung eines Reibkontakts zwischen dem Dämpfungselement (28; 78) und der Laufschaufel (6) vorgesehen ist.Damping system according to one of the preceding claims, wherein an end-face contact surface (70) for producing a frictional contact between the damping element (28; 78) and the moving blade (6) is provided. Dämpfungssystem nach Anspruch 6 oder 7, wobei die Anlageflächen (54, 70) symmetrisch zur Hochachse des Dämpfungselements (28; 78) angeordnet sind.Damping system according to claim 6 or 7, wherein the abutment surfaces (54, 70) are arranged symmetrically to the vertical axis of the damping element (28, 78). Laufschaufel (6) einer Strömungsmaschine mit zumindest einem Dämpfungssystem (26; 74) nach einem der vorhergehenden Ansprüche.Blade (6) of a turbomachine with at least one damping system (26; 74) according to one of the preceding claims. Laufschaufel nach Anspruch 9, wobei stromaufwärts und stromabwärts derselben jeweils ein Dämpfungssystem (26; 74) angeordnet ist.The blade of claim 9, wherein a damping system (26; 74) is disposed upstream and downstream thereof, respectively. Rotor einer Strömungsmaschine mit einer Vielzahl von in Schaufelreihen (2) angeordneten Laufschaufeln (6), wobei an den Laufschaufeln (6) zumindest einer Schaufelreihe (2) jeweils ein Dämpfungssystem (26; 74) nach einem der Ansprüche 1 bis 8 angeordnet ist.Rotor of a turbomachine having a multiplicity of rotor blades (6) arranged in rows of blades (2), wherein a damping system (26; 74) according to any one of claims 1 to 8 is arranged on the rotor blades (6) of at least one row of blades (2).
EP11161054.9A 2010-04-16 2011-04-04 Damping system for damping vibrations of a rotor blade, corresponding rotor blade and rotor Active EP2378068B1 (en)

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EP2378068A3 (en) 2017-12-06
US20110255973A1 (en) 2011-10-20
ES2797494T3 (en) 2020-12-02
DE102010015211A1 (en) 2011-10-20
EP2378066A2 (en) 2011-10-19
EP2378066A3 (en) 2011-12-28
DE102010015211B4 (en) 2013-06-20
US9074479B2 (en) 2015-07-07
EP2378068B1 (en) 2020-04-29

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